CN106573680A - Jet engine cold air cooling system - Google Patents

Jet engine cold air cooling system Download PDF

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Publication number
CN106573680A
CN106573680A CN201580036391.5A CN201580036391A CN106573680A CN 106573680 A CN106573680 A CN 106573680A CN 201580036391 A CN201580036391 A CN 201580036391A CN 106573680 A CN106573680 A CN 106573680A
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CN
China
Prior art keywords
cooling system
air
forecooler
temperature
turbine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN201580036391.5A
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Chinese (zh)
Other versions
CN106573680B (en
Inventor
K.R.利米
B.P.布雷格
M.J.埃普斯坦
J.A.帕里拉
M.J.赫特
T.E.布林森
A.J.弗勒明
G.E.威尔莫特
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General Electric Co
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General Electric Co
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Publication of CN106573680A publication Critical patent/CN106573680A/en
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Publication of CN106573680B publication Critical patent/CN106573680B/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F02C7/185—Cooling means for reducing the temperature of the cooling air or gas
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B64D13/006—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being used to cool structural parts of the aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
    • B64D13/08—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned the air being heated or cooled
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D13/00—Combinations of two or more machines or engines
    • F01D13/02—Working-fluid interconnection of machines or engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/02—Arrangement of sensing elements
    • F01D17/08—Arrangement of sensing elements responsive to condition of working-fluid, e.g. pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
    • B64D2013/0603—Environmental Control Systems
    • B64D2013/0618—Environmental Control Systems with arrangements for reducing or managing bleed air, using another air source, e.g. ram air
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
    • B64D2013/0603—Environmental Control Systems
    • B64D2013/0648—Environmental Control Systems with energy recovery means, e.g. using turbines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
    • B64D2013/0603—Environmental Control Systems
    • B64D2013/0688—Environmental Control Systems with means for recirculating cabin air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/211—Heat transfer, e.g. cooling by intercooling, e.g. during a compression cycle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/213—Heat transfer, e.g. cooling by the provision of a heat exchanger within the cooling circuit
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/606—Bypassing the fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/301—Pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/303—Temperature
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/50—On board measures aiming to increase energy efficiency
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

Methods and devices for cooling systems (100, 700) are provided that are in fluid communication with bleed air from a jet engine compressor. The cooling systems include: a first precooler (210) receiving bleed air from the jet engine compressor; a heat exchanger (730) downstream from the first precooler (210); a cooling system compressor (220) downstream from the first precooler (210), with the heat exchanger (730) and the cooling system compressor (220) being in separate flow paths from the first precooler (210); a cooling system precooler (230) downstream from the cooling system compressor (220); a cooling system turbine (240) with variable guide vanes (VGT) and downstream from the cooling system precooler (230); and a discharge conduit (245) downstream from the cooling system turbine (240) and the heat exchanger (730). A bypass line (290) can also be included that bypasses the cooling system turbine (240).

Description

Jet engine cold air cooling system
Priority information
Entitled " the Jet Engine Cold Air that Leamy etc. was submitted on July 3rd, 2014 are enjoyed in the application request U.S. Provisional Patent Application and Leamy of the Serial No. 62/020512 of Cooling System " etc. were on July 9th, 2014 The U.S. of the Serial No. 62/022364 of entitled " the Jet Engine Cold Air Cooling System " that submit to is interim The priority of patent application, disclosures of which is herein incorporated by reference.
The field of the invention
Present disclosure is related to jet engine, and relates more specifically to be released using jet engine air come for cooling down The heat load that the delivery vehicle coupled with engine or engine is associated.
The background of the present invention
Modern jet plane by the air stream of regulation from jet engine guide to the occupancy of aircraft cabin and other Region.The commonly referred to deflationary air stream can be obtained from high pressure compressor (HPC) section of jet engine.The U.S. is special Profit No. 5137230 and No. 5125597 describes to be guided before cabin introducing to further process for will release air Conventional structure and method in the environmental control system (ECS) of deflationary aircraft.ECS combines each part equipment, such as empty Gas circulator (ACM), regulating valve, heat exchanger and miscellaneous equipment, to adjust engine bleed air before cabin is introduced.
Releasing air is usually used the stream of regulation and obtains from multiple positions along HPC sections, to control to obtain deflationary Degree.Have in adjustment structure and operate into the check-valves for allowing or stopping air stream, and reduced what is obtained before it reaches ECS The downstream damper of deflationary pressure.The releasing air of the reduction pressure is directed to turbine, and work(is obtained in this place, wherein Releasing air outlet slit pressure and temperature from turbine is substantially reduced.The releasing air of the reduction pressure keeps relatively hot, and Subsequently cooled down by the fan air in the heat exchanger being associated with jet engine of commonly referred to forecooler.From forecooler output The releasing air of cooling be delivered to ECS, in this place, it can enter before the cabin of occupancy of aircraft or other regions is introduced One step is cooled down and pressure is further adjusted.In addition to by releasing air supply to ECS, jet engine provides low-temperature receiver, its offer Precooled air is to aircraft and back as a part of high temperature air received from aircraft of circulation.
No matter using what structure or method, keeping invariably relative to the releasing air of supply to ECS：Compare and flow through The air of the minimum temperature of jet engine can not be lower in temperature.Additionally, release air always using flow control valve from HPC is adjusted, and flow control valve limits air stream and operates into and gradually reduced releasing air pressure before forecooler is reached.Cause This, needed for this area is will to release air be less than at a temperature of the air of the minimum temperature for flowing through jet engine in addition It is delivered to the structures and methods of ECS.
The brief description of the present invention
Aspects and advantages of the present invention will be illustrated in the following description, or can be clear from description, or can be by implementing the present invention Understand.
Generally provide and the cooling system that air fluid is connected of releasing from jet engine compressor.
In one embodiment, cooling system includes：Connect with the releasing air fluid from jet engine compressor The first forecooler；It is in fluid communication with the first forecooler and in the heat exchanger in the first forecooler downstream；With the first forecooler fluid Connect and in the cooling system compressor in the first forecooler downstream, wherein heat exchanger and cooling system compressor are from the first precooling In the separate flow passage of device；Connect with cooling system compressor fluid and the cooling system in cooling system compressor downstream is pre- Cooler；It is in fluid communication with cooling system forecooler and in the cooling system turbine in cooling system forecooler downstream；And in cooling System Turbo and the discharge tube in heat exchanger downstream.
In another embodiment, cooling system includes：Connect with the releasing air fluid from jet engine compressor The first logical forecooler；It is in fluid communication with the first forecooler and in the cooling system compressor in the first forecooler downstream；With cooling System compressors are in fluid communication and in the cooling system forecooler in cooling system compressor downstream；With cooling system forecooler fluid Connect and in the cooling system turbine in cooling system forecooler downstream；In the discharge tube in cooling system turbine downstream；And with Cooling system forecooler is in fluid communication and in the bypass line in cooling system forecooler downstream.Bypass line and discharge tube fluid Connection and in discharge tube upstream, and provide cooling system turbine entrance side and waste side between selectivity be in fluid communication with Bypass cooling system turbine.
Jet engine is additionally provided, it includes：Engine compressor；The burning connected with engine compressor flowing Device；Connect to receive the engine turbine of the combustion product from burner with combustor flow；And with from engine pressure The cooling system as described above for releasing air fluid connection of contracting machine.Aircraft includes such jet engine and flight At least one of device heat management system and aircraft environment control system, wherein discharge tube and aircraft heat management system and At least one of aircraft environment control system is in fluid communication.
Deflationary method in generally additionally providing for cooling down jet engine.In one embodiment, should Method includes：Releasing air is obtained from jet engine compressor；Air will be released to guide to the first forecooler, wherein releasing empty Gas has acquisition temperature；Deflationary acquisition temperature is reduced to into second temperature in the first forecooler；Hereafter, will release empty The Part I of gas is guided to heat exchanger and deflationary Part II is guided to cooling system compressor so that first Divide and Part II limits separate flow passage；Deflationary Part I is set to flow through heat exchanger with by the of Part I Two temperature are reduced to the 3rd temperature；Deflationary Part II is set sequentially to flow through cooling system compressor, cooling system precooling Device and cooling system turbine by the second temperature of Part II to be reduced to the 4th temperature, wherein the 4th temperature is warm less than obtaining Degree；And hereafter, Part I and Part II are mixed in discharge tube.
These and other feature of the present invention, aspect and advantage will become more preferable with reference to the following description and the appended claims Understand.The accompanying drawing for the part for being attached in this specification and constituting specification shows embodiments of the invention, and together with retouching State the principle for explaining the present invention.
The brief description of accompanying drawing
Exist for the complete and open disclosure of the invention including its optimal mode of one of ordinary skill in the art Propose in specification referring to the drawings, in the accompanying drawings：
Fig. 1 is the schematic diagram of the exemplary embodiment of the cold air cooling system for the part for being shown as aircraft by way of example；
Fig. 2 is the signal of another exemplary embodiment of the cold air cooling system for the part for being shown as aircraft by way of example Figure；
Fig. 3 is showing for also another exemplary embodiment of the cold air cooling system for the part for being shown as aircraft by way of example It is intended to；
Fig. 4 is the signal of another exemplary embodiment of the cold air cooling system for the part for being shown as aircraft by way of example Figure；
Fig. 5 is showing for also another exemplary embodiment of the cold air cooling system for the part for being shown as aircraft by way of example It is intended to；
Fig. 6 is the elevation perspective of the aircraft of the combination cold air cooling system according to present disclosure；And
Fig. 7 shows cutting for one embodiment that can be used for the gas-turbine unit in aircraft of the aspect according to this theme Face view.
Fig. 8 shows the diagram of the illustrative methods embodied by the aspect of this theme.
Fig. 9 shows the diagram of the another exemplary method embodied by the aspect of this theme.
The detailed description of the present invention
Embodiments of the invention are reference will now be made in detail to now, and one or more example is shown in the drawings.Each example is by explaining The mode for releasing the present invention is provided and does not limit the present invention.In fact, those skilled in the art will be clear that, without departing from this In the case of the scope or spirit of invention, can in the present invention various modifications may be made and modification.For example, it is illustrated or described as one The feature of a part for embodiment can be used with another embodiment to produce another embodiment.It is therefore intended that this It is bright to cover the such remodeling in the range of being included into claims and its equivalent and modification.
As used herein term " first ", " second " and " the 3rd " is used interchangeably with by a component and another area Separate, and be not intended to represent position or the importance of individual member.In addition, term " upstream " and " downstream " are referred to relative to fluid The relative direction of the fluid stream in path.For example, " upstream " refers to the direction that fluid flows from it, and " downstream " refers to that fluid flow to Direction.
Generally provide cold with the releasing air that the releasing air fluid of the compressor in jet engine is connected But system.Release air cooling system and be generally configured into the releasing air that cooling is received, and air (for example, the Jing that will be cooled down By from the discharge tube for releasing air cooling system) provide into aircraft heat management system and aircraft environment control system At least one.In one embodiment, have from the air of the cooling of cooling system output and be less than into and through engine Air average flowing passage temperature temperature.Generally additionally provide the fluid (for example, the air of cooling) that cooling is provided Method, wherein input air obtains (for example, from the releasing air of engine compressor) from jet engine.
Referring to Fig. 1 and Fig. 6, the first exemplary cold air cooling system 100 is configured to from the height of jet engine 112 The unadjusted releasing air of pressure compressor (HPC) is less than providing to aircraft 122 at a temperature of engine airflow 110 Aircraft heat management system and/or environmental control system (ECS) 121.For the purpose of present disclosure, engine cool stream bag Include and be not limited to one of following or many persons：Fan flow air, the intake air of suction air inlet and ram-air.According to following Exemplified, the system 100 of jet engine 112 will be described as the structural fluid connection being associated with same aircraft 122.
Referring to Fig. 1 and Fig. 6, conventional heat pipe reason system (TMS) loop 150 is used to for heat energy to deflect from aircraft 122, and by this Heat energy conveys/is pumped to jet engine TMS 170.For those structures for will being associated with aircraft 122 and engine 112 Structure more preferably distinguish, depict dotted line 124.Therefore, the structure on the right side of dotted line 124 is drawn by way of example and is described as A part for engine 112, and those structures in the left side of dotted line 124 are drawn by way of example and are described as and engine 112 Separate and be associated with aircraft 122.It is to be understood, however, that some components being associated with aircraft 122 can be changed to send out A part for motivation 112, and vice versa.Therefore, those skilled in the art is it should be appreciated that structure and be described in essence On be exemplary, and the determination of the structure of a part for the part as engine 112 or aircraft 122 is not restricted 's.
Referring to Fig. 1, exemplary cold air cooling system 100 is shown, and it includes the HPC sections from engine 112 Unadjusted releasing air intake supply 200.Releasing air intake supply 200 by high pressure and high temperature compressed air supply to First forecooler 210.In exemplary form, first forecooler 210 is easy to for heat energy to release air biography from high pressure and high temperature The cooler air being handed in suction engine 112.There can be significantly reduced temperature from the releasing air of the output of forecooler 210, But its pressure is not significantly changed.The pressure-air of the lower temperature is supplied in cooling system compressor 220, and it raises air Temperature and pressure.Therefore, from compressor 220 output air significantly more pressurization and in temperature higher than output to compressor Air.Guide to cooling system forecooler 230 from the high temperature air of the very high pressure of compressor output.For example, it is cold But system precooler 230 is easy to be transferred to suck the stream in engine 112 from the air of releasing of very high pressure and high temperature by heat energy Dynamic passage temperature air.There is significantly reduced temperature from the releasing air of the output of cooling system forecooler 230, but it is very high Pressure will not be significantly changed.From cooling system forecooler 230 output this very high pressure, lower temperature releasing air guiding To in the cooling system turbine 240 with Variable Area turbine nozzle (VATN).It is noted, however, that multiposition turbine Nozzle or the alternative Variable Area turbine nozzle of FX turbine nozzle are used.Put by the very high pressure of rotation turbine 240 Going out the work(of air execution is used for the energy supply of compressor 220, wherein the releasing air for exporting has significantly reduced pressure and temperature. It should be appreciated by those skilled in the art that turbine 240 mechanically or fluidly links to compressor 220, to transmit by expanding through The work(that the air of the very high pressure of turbine is produced.
In exemplary form, export the deflationary temperature in discharge tube 245 from turbine 240 and send out less than entering The average flowing passage temperature of the air in motivation 112.This is obvious with the releasing air cooling system of prior art conversely, existing The releasing air cooling system of technology can not release air in the temperature less than the average flowing passage temperature into engine 112 Aircraft 122 is delivered under degree.
As shown in Figure 2, alternative exemplary cold air cooling system 280 includes the first exemplary cold air cooling system 100 structure, and be for illustration purposes only, will be illustrated as being used with reference to the TMS circulations 150 in the first exemplary embodiment.Cause This, similar reference number represents the analog structure such as discussed according to the first exemplary embodiment, and will not repeat to promote letter It is clean.
In addition to the structure of the first exemplary cold air cooling system, the first alternate exemplary cold air cooling system 280 Including bypass line 290 and the control valve 292 connected with bypass line.In exemplary form, bypass line 290 is connected to whirlpool Between the entrance of wheel 240 and outlet, guided to ECS with the air selectively allowed for from the discharge of cooling system forecooler 230 121 and do not travel across turbine.For example, control valve 292 to be communicably coupled to and the air thermal communication discharged from turbine 240 Thermocouple (not shown).
Depending on engine 112 and the operating condition of surrounding air property (temperature, pressure etc.), it can be advantageous that have The releasing air of bypassed turbine 240.For example, if too low from the temperature of the air of the discharge of turbine 240, control valve 292 can be from Thermocouple receives temperature reading, and based on program parameter, opens or closes the valve connected with bypass line 290, to convey Deflationary temperature to aircraft 122 is improved and controlled within a predetermined range.Alternatively, or additionally, controlling valve 292 can be with Pressure sensor communication at the floss hole of turbine 240.In the case of discharge pressure is too low, control valve 292 can be passed from pressure Sensor receives pressure reading, and based on program parameter, opens or closes the valve connected with bypass line 290, to be delivered to The deflationary pressure of aircraft 122 is improved and controlled within a predetermined range.Although aforesaid by-pass is described as having actively managing Reason, but it will be appreciated by persons skilled in the art that passive management is equally possible.
As shown in Figure 3, another alternate exemplary cold air cooling system 700 includes the first alternate exemplary cold air The structure of cooling system 280.Therefore, similar reference number is represented such as according to the similar of the first alternative exemplary embodiment discussion Structure, and will not repeat succinct to promote.
In addition to the structure of the first alternate exemplary cold air cooling system 280, another alternate exemplary cold air is cold But system 700 includes bypass line 710, and in the outlet side downstream of the first forecooler 210 and control in flow communication Valve 720.In exemplary form, bypass line 710 is connected between the outlet of heat exchanger 730 and the outlet of turbine 240, to select The air from the discharge of heat exchanger 730 is allowed to selecting property to guide to the downstream of turbine 240.Heat exchanger 730 is received in suction engine 112 Average flowing passage air, and using the air as low-temperature receiver come by heat energy from flow out the first forecooler 210 higher temperature Air transmission.For example, control valve 720 is communicably connected to the thermoelectricity with the air thermal communication discharged from turbine 240 Even (not shown).Alternatively, control valve 720 can passively control and be positioned at the downstream of heat exchanger 730, so as to improve be delivered to it is winged The temperature and/or pressure of the air of row device 122.
Drain valve 712 is optionally positioned in bypass line 710 and is in fluid communication with heat exchanger 730, and in heat exchanger 730 downstreams, but in the upstream of discharge tube 245.Drain valve 712 is configured to control from heat exchanger 730 to the fluid of discharge tube 245 Stream.Drain valve 712 can receive temperature reading from thermocouple, and based on program parameter, open or close and connected with bypass line 710 Valve, so as to will be delivered to aircraft 122 deflationary temperature improve and control within a predetermined range.Alternatively or this Outward, drain valve 712 can be with the pressure sensor communication at the floss hole of turbine 240.In the case of discharge pressure is too low, discharge Valve 712 can receive pressure reading from pressure sensor, and based on program parameter, open or close what is connected with bypass line 710 Valve, to improve and controlling within a predetermined range the deflationary pressure for being delivered to aircraft 122.Although aforesaid by-pass is retouched State is that, with active management, but it will be appreciated by persons skilled in the art that passive management is equally possible.
Depending on engine 112 and the operating condition of surrounding air property (temperature, pressure etc.), it can be advantageous that make to put Go out air by-pass turbine 240.For example, if too low from the temperature of the air of the discharge of turbine 240, control valve 720 can be from thermoelectricity Shrinkage temperature reading is coupled, and based on program parameter, opens or closes the valve connected with bypass line 710, to will be delivered to fly The deflationary temperature of row device 122 is improved and controlled within a predetermined range.Alternatively, or additionally, controlling valve 720 can be with turbine Pressure sensor communication at 240 floss hole.In the case of discharge pressure is too low, control valve 720 can be from pressure sensor Pressure reading is received, and based on program parameter, opens or closes the valve connected with bypass line 710, so that flight will be delivered to The deflationary pressure of device 122 is improved and controlled within a predetermined range.
Referring to Fig. 4, the second exemplary cold air cooling system 300 is configured to from the high pressure pressure of jet engine 112 The unadjusted releasing air of contracting machine (HPC) section is supplied at a temperature of less than the temperature for flowing into the air in engine 112 To aircraft 122.Exclusively for the purposes of illustration, the second exemplary cold air cooling system 300 will be illustrated as with reference to from first The TMS circulations 150 of exemplary embodiment are used.Therefore, similar reference number is represented such as according to the first exemplary embodiment opinion The analog structure stated, and will not repeat succinct to promote.
As the first exemplary embodiment, the second exemplary cold air cooling system 300 is included from engine 112 HPC sections unadjusted releasing air intake supply 400.Releasing air intake supply 400 is by high pressure and high temperature compressed Air supply is to the first forecooler 410.In exemplary form, first forecooler 410 is easy to heat energy from high pressure and high temperature Release air to be transferred to suck the air in engine 112.Can have from the releasing air of the output of forecooler 410 significantly reduced Temperature, but its pressure will not significantly change.The pressure-air of the lower temperature is supplied to Variable Area turbine nozzle In turbine 440.Just as in prior embodiments, Variable Area turbine nozzle can be by multiposition turbine nozzle or FX turbine Nozzle is replaced.
By the high pressure of rotation turbine 440 release the work(that air performs can be used for it is pair related to engine 112 or aircraft 122 The miscellaneous equipment energy supply of connection, wherein the releasing air for exporting has significantly reduced pressure and temperature.For example, turbine 440 Can be used to rotate with making the energy supply of generator 475 gear mechanism of gear-box 480, transfer tube 485, or for transmitting and starting Any combinations of the aforementioned mechanical device of the associated work(of machine 112 or aircraft 122.It should be appreciated by those skilled in the art that It is that turbine 440 mechanically or is fluidly linked to one or more in aforementioned components, with using the high pressure by revolving wormgear Release the work(that air is performed.In exemplary form, the deflationary temperature from the output of turbine 440 is less than outflow forecooler The flow passage temperature of 410 air.This releases air cooling system substantially conversely, prior art is put with prior art again Going out air cooling system can not release air conveying at a temperature of less than the environment flowing passage air into engine 112 To aircraft 122.
Referring to Fig. 5, the 3rd exemplary cold air cooling system 500 is configured to from the high pressure pressure of jet engine 112 The unadjusted releasing air of contracting machine (HPC) section is supplied at a temperature of less than the temperature for flowing into the air in engine 112 To aircraft 122.Exclusively for the purposes of illustration, the 3rd exemplary cold air cooling system 500 will be illustrated as with reference to from first The TMS circulations 150 of exemplary embodiment are used.Therefore, similar reference number is represented such as according to the first exemplary embodiment opinion The analog structure stated, and will not repeat succinct to promote.
As the first exemplary embodiment, the 3rd exemplary cold air cooling system 500 is included from engine 112 HPC sections unadjusted releasing air intake supply 600.Releasing air intake supply 600 is by high pressure and high temperature compressed Air supply is to the first forecooler 610.In exemplary form, first forecooler 610 is easy to heat energy from high pressure and high temperature Release air to be transferred to suck the air in engine 112.Can have from the releasing air of the output of forecooler 610 significantly reduced Temperature, but its pressure will not significantly change.The pressure-air of the lower temperature is supplied to Variable Area turbine nozzle In turbine 640.Just as in prior embodiments, multiposition turbine nozzle or the alternative Variable Area whirlpool of FX turbine nozzle Wheel nozzle is used.
By the high pressure of rotation turbine 640 release the work(that air performs can be used for it is pair related to engine 112 or aircraft 122 The miscellaneous equipment energy supply of connection, wherein the releasing air for exporting has significantly reduced pressure and temperature.For example, turbine 640 For to the energy supply of compressor 650 on the outlet side of engine cooling apparatus 660.For example, engine cooling apparatus 660 are via entering Mouthfuls 670 inhalation flow passage temperature air under a predetermined.Flow passage temperature air as low-temperature receiver by heat deflect from it is cold But the thermal source that device 600 is associated, and flow out cooler under the pressure less than the outlet pressure floss hole 680 of compressor 650.Across The pressure reduction of overcompression machine 650 operates into and draws air into compressor and eventually pass through entrance 670.Those skilled in the art will manage Solve, turbine 640 mechanically or fluidly links to compressor 650, held with releasing air using the high pressure by revolving wormgear Capable work(.In exemplary form, the deflationary temperature from the output of turbine 640 is less than the air for flowing out forecooler 610 Flow passage temperature.This is obvious conversely, the releasing air of prior art is cold with the releasing air cooling system of prior art again But system can not release air less than being transported in aircraft 122 at a temperature of the air of engine 112.Additionally, Releasing air output (that is, exporting fluid) can have the approximately half of output temperature (example for being less than deflationary acquisition temperature Such as, less than obtain temperature about three/mono-).
Referring to Fig. 8, show and provide exemplary to the aircraft heat management system with heat load by the air of regulation Method 800.The method is included at 802 from jet engine to the reception and cooling in the first forecooler.Generally, do not adjust Air there is input pressure and input temp when receiving in the first forecooler.Then, the first forecooler will can not adjusted Air be cooled to the first temperature.The Part I 803 of unadjusted air then can be (for example, cold via compressor at 804 But system compressors) compressor is to first pressure.Then the Part I of unadjusted air can alternatively cool down at 806 (for example, in cooling system forecooler).Then the Part I of unadjusted air is received with Variable Area at 808 In the turbine of turbine nozzle (for example, in cooling system turbine).The Part II 809 of unadjusted air at 810 via Second forecooler is cooled to second temperature.As illustrated, the second of the Part I of unadjusted air and unadjusted air Part is in separate flow passage.Finally, the Part I of the unadjusted air in the Part II of unadjusted air Adjusted to the exhaust temperature and discharge for being chosen to the requirement for meeting aircraft heat management system by obtaining work(from turbine at 812 Pressure.In certain embodiments, the work(of acquisition can be provided to for transmitting the mechanical device of work(, such as compressor, gear-box, sent out Motor or pump.
Referring to Fig. 9, show and provide exemplary to the aircraft heat management system with heat load by the air of regulation Method 900.The method is included at 902 from jet engine to the reception and cooling in the first forecooler.Generally, do not adjust Air there is input pressure and input temp when receiving in the first forecooler.Then, the first forecooler will can not adjusted Air be cooled to the first temperature.Unadjusted air then at 904 via compressor (for example, in cooling system compressor In) it is compressed to first pressure.Then, the unadjusted air of compression can alternatively be cooled down (for example, in cooling system at 906 In system forecooler).Then the Part I 907 of unadjusted air receives at 908 and is expanded into Variable Area turbine In the turbine of nozzle.The Part II 909 of unadjusted air is at 910 from cooling system compressor bypass turbine.In discharge In pipeline, the Part II of the Part I of unadjusted air and unadjusted air is at 912 by obtaining work(from turbine Adjust to the exhaust temperature and discharge pressure for being chosen to the requirement for meeting aircraft heat management system.In certain embodiments, obtain Work(can provide to for transmitting the mechanical device of work(, such as compressor, gear-box, generator or pump.
In this method, the first forecooler and the second forecooler can use the fan flow air conduct from jet engine Low-temperature receiver fluid, wherein fan flow air have fan flow temperature and fan flowing pressure.In one embodiment, exhaust temperature is less than Fan flow temperature.For example, jet engine can under the static conditions of sea level with idling higher than about 17psi and/or Fan flow pressure operation when taking off higher than about 30psi.
The air of regulation can provide the reduction more than about 10% of the heat load of aircraft heat management system, it is all such as larger than About 60%.For example, the heat load that the air of regulation can be provided the heat load of about 90kW more than about 4kW is reduced.
It is noted, however, that the air in addition to flow passage air can be used as forecooler 210,230,410,610, Any one of 730 low-temperature receiver.Additionally, although foregoing example embodiment has been described as including forecooler, it is to be understood that It is that forecooler and heat exchanger are synonymous.
Although it is to be further understood that system 100,280,300,500,700 have been described as it is related to jet engine 112 Connection, but also scope of the present disclosure interior is to make these systems be in fluid communication to come for waterborne or land with other delivery vehicles On the ground (for example, ship or motor vehicles).
Fig. 7 shows a reality of the gas-turbine unit 112 that can be used in aircraft of the aspect according to this theme The section view of example is applied, wherein engine 112 is shown as having the longitudinally or axially center for extending through for reference purposes therebetween Bobbin thread 12.Although illustrated as turbofan jet engine, but any suitable jet engine all can be with reference to cooling as herein described System is used.For example, suitable jet engine include but is not limited to high by-pass turbofan engine, low by-pass turbofan engine, Turbojet, turboprop, turboaxle motor, propeller fan engine etc..
As shown in Figure 7, exemplary engine 112 may include fan (generally by reference number 14 point out) and it is positioned on the fan section 16 swum.Core-engine 14 generally may include to limit the big of annular entry 20 Cause the shell 18 of tubulose.Additionally, shell 18 can also surround and support booster compressor 22, for will be into core-engine 14 Air pressure rise to first pressure level.Then high pressure, multistage, Axial Flow Compressor 24 can connect from booster compressor 22 Forced air is received, and further raises the pressure of this air.Flow out the forced air of high pressure compressor 24 and then burning can be flow to Device 26, fuel is ejected in forced air stream in burner 26, mixture burning in burner 26 of gained.High-energy combustion Product is guided to first (high pressure) turbine 28 for (high via first from burner 26 along the hot gas path of engine 10 Pressure) power transmission shaft 30 drives high pressure compressor 24, and second (low pressure) turbine 32 is then directed to for via generally with the Coaxial second (low pressure) power transmission shaft 34 of one power transmission shaft 30 drives booster compressor 22 and fan section 16.Driving each turbine After 28 and 32, combustion product can eject offer propulsion jet thrust via exhaust nozzle 36 from core-engine 14.
Additionally, as shown in Figure 7, the fan section 16 of engine 10 can generally include rotatable tube-axial fan and turn Son 38, it is configured to be wrapped by ring-type fan shell 40.One of ordinary skill in the art will be recognized that fan hub 40 may be configured to Supported by multiple circumferentially-spaced export orientation stators 42 opened for substantially radially extending relative to core-engine 14.Therefore, Fan hub 40 can surround fan propeller 38 and its corresponding fan rotor blade 44.Additionally, the downstream section 46 of fan hub 40 can The outside extension of core-engine 14 is crossed, to limit the auxiliary or bypath air flow tube road that provide additional propulsion jet thrust 48。
During the operation of engine 10, it is to be appreciated that initial air stream (being pointed out by arrow 50) can pass through wind The associated entrance 52 of fan case 40 enters engine 10.Air stream 50 then passes through fan blade 44, and is divided into and moving through First compressed air stream (being pointed out by arrow 54) of pipeline 48 and into booster compressor 22 the second compressed air stream (by arrow 56 point out).The pressure of the second compressed air stream 56 and then increase and into high pressure compressor 24 (as arrow 58 is pointed out).With combustion Material mixes and after burning in burner 26, and combustion product 60 flows out burner 26 and flows through the first turbine 28.Hereafter, burn Product 60 flows through the second turbine 32 and flows out exhaust nozzle 36 to provide thrust to engine 10.
As used herein flow passage temperature refers to that fluid (that is, air) flows through the fate of jet engine at it Median temperature during section/level.More specifically, flow passage temperature compare suction jet engine air inlet air most Low temperature can not be lower.When air sucks air inlet and compresses, air will be raised in temperature, and therefore with compressor area Flow passage temperature near the end of section, it is higher than the flow passage temperature of the air at air inlet.
Although it is to be further understood that describing foregoing example embodiment, this public affairs in the background of aircraft Drive the delivery vehicle that content is equally applicable in addition to aircraft.Any delivery vehicle needed with cabin or other coolings all may be used Solved using present disclosure.For example, the ship of jet energy supply can benefit from the exemplary embodiment of present disclosure, with to cabin And/or the electronic installation being associated with ship provides cooling.Therefore, foregoing disclosure is not limited to be applied to aircraft, but Any delivery vehicle suitable for providing cooling stream using jet power in any usefulness.Those skilled in the art will hold Easily recognize effectiveness of the present disclosure in the background of other delivery vehicles.
As described above, one of ordinary skill in the art will be clear that, although methods and apparatuses described herein Constitute the exemplary embodiment of present disclosure, it is to be understood that the disclosure for including herein to be not limited to the above definitely real Apply example, and can without departing from scope of the present disclosure in the case of make change.Similarly, it will be appreciated that be, it is not necessary to The advantage or purpose of any or all of determination of present disclosure are met to fall within the scope of this disclosure, because can There is the intrinsic and/or unpredictalbe advantage of present disclosure, even if they may clearly not discussed herein.

Claims (27)

1. the cooling system that a kind of releasing air fluid with from jet engine compressor is connected, the cooling system bag Include：
With the first forecooler that air fluid is connected of releasing from the jet engine compressor；
It is in fluid communication with first forecooler and in the cooling system compressor in the first forecooler downstream；
Connect with the cooling system compressor fluid and in the cooling system forecooler in the cooling system compressor downstream；
It is in fluid communication with the cooling system forecooler and in the cooling system turbine in the cooling system forecooler downstream；
In the discharge tube in the cooling system turbine downstream；And
It is in fluid communication with the cooling system forecooler and in the bypass line in the cooling system forecooler downstream, wherein described Bypass line is in fluid communication and in the discharge tube upstream with the discharge tube, and wherein described bypass line provides described Selectivity between the entrance side and waste side of cooling system turbine is in fluid communication to bypass the cooling system turbine.
2. cooling system according to claim 1, it is characterised in that the cooling system turbine has Variable Area turbine Nozzle.
3. cooling system according to claim 2, it is characterised in that the Variable Area turbine nozzle construction into control from Fluid stream of the cooling system turbine to the discharge tube.
4. cooling system according to claim 1, it is characterised in that the cooling system also includes：
The control valve connected with the bypass line.
5. cooling system according to claim 4, it is characterised in that the control valve is configured to control through the bypass The fluid stream of circuit is bypassing the cooling system turbine.
6. cooling system according to claim 1, it is characterised in that the releasing air has and obtains temperature, and wherein The discharge tube provides the output fluid having less than the deflationary approximately half of output temperature for obtaining temperature.
7. cooling system according to claim 1, it is characterised in that first forecooler and the cooling system precooling Device uses fan flow air from the jet engine as low-temperature receiver fluid, and the fan flow air has fan flow temperature With fan flowing pressure, and wherein the discharge tube provides the output stream with the output temperature less than the fan flow temperature Body.
8. cooling system according to claim 1, it is characterised in that the cooling system also includes：
Be in fluid communication with first forecooler and in the heat exchanger in the first forecooler downstream, and wherein described heat exchanger with The cooling system compressor fluid is connected and in the cooling system upstream of compressor.
9. cooling system according to claim 1, it is characterised in that the cooling system also includes：
Be in fluid communication with first forecooler and in the heat exchanger in the first forecooler downstream, and wherein described heat exchanger and The cooling system compressor is from the separate flow passage of first forecooler.
10. cooling system according to claim 9, it is characterised in that the cooling system also includes：
It is in fluid communication with first forecooler and in the control valve in the first forecooler downstream, wherein the control valve includes Connect with the heat exchanger fluid and in the first outlet of the heat exchanger upstream, and wherein it is described control valve include it is cold with described But system Turbo is in fluid communication and in the second outlet of the cooling system turbine upstream, and further wherein described control valve structure Cause to adjust to the control fluid stream of each in the heat exchanger and the cooling system turbine.
Deflationary method in a kind of 11. cooling jet engines, methods described includes：
Releasing air is obtained from jet engine compressor；
The releasing air is guided to the first forecooler, wherein the releasing air has obtains temperature；
The deflationary acquisition temperature is reduced to into second temperature in first forecooler；
Hereafter, the deflationary Part I is guided to cooling system compressor；
The releasing air is set sequentially to flow through the cooling system compressor and cooling system forecooler；
The deflationary Part I is set to flow in cooling system turbine to put described from the cooling system forecooler The second temperature for going out the Part I of air is reduced to the 3rd temperature, wherein the 3rd temperature is less than the second temperature；
The deflationary Part II is set to flow through bypass line from the cooling system forecooler；And
Hereafter, the Part I and the Part II are mixed in discharge tube.
12. methods according to claim 11, it is characterised in that methods described also includes：
Control the flow through the Part I of the cooling system turbine.
13. methods according to claim 12, it is characterised in that there is the cooling system turbine Variable Area turbine to spray Mouth is controlling the flow through the cooling system turbine.
14. methods according to claim 11, it is characterised in that methods described also includes：
Control the flow through the Part I of the cooling system turbine.
15. methods according to claim 14, it is characterised in that control valve is connected with the bypass line.
16. methods according to claim 15, it is characterised in that the control valve is configured to control through the bypass line The fluid stream on road is bypassing the cooling system turbine.
17. methods according to claim 11, it is characterised in that the releasing air has acquisition temperature, and wherein institute State discharge tube and the output fluid having less than the deflationary approximately half of output temperature for obtaining temperature is provided.
18. methods according to claim 11, it is characterised in that first forecooler and the cooling system forecooler Using the fan flow air from the jet engine as low-temperature receiver fluid, the fan flow air have fan flow temperature and Fan flowing pressure, and wherein described discharge tube provides the output fluid with the output temperature less than the fan flow temperature.
19. a kind of provide the air of regulation to the method for the aircraft heat management system with heat load；Methods described includes：
By in the unadjusted air receiver of jet engine to the first forecooler, the unadjusted air has input Pressure and input temp；
The unadjusted air is cooled to into the first temperature in first forecooler；
By the unadjusted air via compressor compresses to first pressure；
The unadjusted air is cooled to into second pressure via cooling system forecooler；
By the Part I of the unadjusted air in the cooling system compressor accepted downstream to Variable Area whirlpool In the turbine of wheel nozzle；
The Part I for making the unadjusted air expands and in discharge tube in the turbine；
The Part II of the unadjusted air is made in the cooling system compressor downstream bypass to the discharge tube； And
It is chosen to meet the flight by obtaining work(from the turbine and being expanded to the Part I of the unadjusted air The exhaust temperature and discharge pressure of the requirement of device heat management system.
20. methods according to claim 19, it is characterised in that first forecooler and the cooling system forecooler Using the fan flow air from the jet engine as low-temperature receiver fluid, the fan flow air have fan flow temperature and Fan flowing pressure.
21. methods according to claim 20, it is characterised in that the exhaust temperature is less than the fan flow temperature.
22. methods according to claim 19, it is characterised in that the jet engine is in sea level static state idle condition It is lower operation and the fan flowing pressure be higher than about 17psi.
23. methods according to claim 19, it is characterised in that the jet engine is in sea level static state takeoff condition It is lower operation and the fan flowing pressure be higher than about 30psi.
24. methods according to claim 19, it is characterised in that the work(of acquisition is provided to the machinery for transmitting work(and filled Put, described device selected from compressor, gear-box, generator and pump group into group.
25. methods according to claim 19, it is characterised in that the air of the regulation provides the heat more than about 10% Load reduction.
26. methods according to claim 19, it is characterised in that the air of the regulation provides the heat more than about 60% Load reduction.
27. methods according to claim 19, it is characterised in that the air of the regulation provides about 4kW to about The heat load of 90kW is reduced.
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